Aircraft electric or hybrid propulsion architecture

Abstract

An aircraft electric or hybrid propulsion architecture including at least two propulsion lines, each propulsion line including at least one electric motor supplied from at least two energy sources of the propulsion architecture through at least two energy supply paths, each energy supply path including at least one energy inverter, and one electrical protection delivering a DC voltage for a HVDC bus, each HVDC bus distributing this DC voltage to at least one electric motor through at least one energy inverter and one electrical protection, the propulsion architecture including at least partially dissimilar and preferably completely dissimilar energy supply paths.

1 . An aircraft electric or hybrid propulsion architecture including at least two propulsion lines, each propulsion line including at least one electric motor supplied from at least two energy sources of the propulsion architecture through at least two energy supply paths, each energy supply path including at least one energy inverter and one electrical protection delivering a DC voltage for a HVDC bus, each HVDC bus distributing this DC voltage to at least one electric motor through at least one of said energy inverters and one of said electrical protections,
 the propulsion architecture being characterized in that the energy source, the energy inverter, the electrical protection and the HVDC bus of one energy supply path are each dissimilar, respectively, from the energy source, from the energy inverter, from the electrical protection and from the HVDC bus of at least one other energy supply path.   
     
     
         2 . The architecture as claimed in  claim 1 , wherein the electric motors of the at least two propulsion lines are dissimilar. 
     
     
         3 . The architecture as claimed in  claim 1 , further including an electrical bus protection set up between two dissimilar HVDC buses. 
     
     
         4 . The architecture as claimed in  claim 3 , wherein the electrical bus protection comprises a series assembly of a controlled elementary electrical protection, preferably comprising a contactor, and a non-controlled elementary electrical protection, preferably comprising a circuit breaker. 
     
     
         5 . The architecture as claimed in  claim 1 , the architecture being configured to be applied to a ring energy distribution network with three HVDC buses, wherein at least one HVDC bus is partially or completely dissimilar from the two others. 
     
     
         6 . The architecture as claimed in  claim 1 , the architecture being configured to be applied to a ring energy distribution network with four HVDC buses, wherein at least one HVDC bus is partially or completely dissimilar from the three others. 
     
     
         7 . The architecture as claimed in  claim 5 , wherein two adjacent HVDC buses of the energy distribution network are connected to one another by a series assembly of two electrical bus protections. 
     
     
         8 . The architecture as claimed in  claim 7 , wherein each of said two electrical bus protections comprises two dissimilar elementary electrical protections, preferably one controlled elementary electrical protection and one non-controlled elementary electrical protection. 
     
     
         9 . An electric or hybrid aircraft including an electric or hybrid propulsion architecture as claimed in  claim 1 .